Device and method for testing the integrity of a helicopter turbine engine rapid restart system

Patent metadata

Field	Value
Publication number	US-10253699-B2
Application number	US-201515514320-A
Country	US
Kind code	B2
Filing date	Sep 21, 2015
Priority date	Sep 29, 2014
Publication date	Apr 9, 2019
Grant date	Apr 9, 2019

Abstract

A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, includes a pneumatic turbine that is mechanically connected to the turboshaft engine and is supplied with gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate the turboshaft engine and ensure that it is reactivated. The testing device has an apparatus configured to withdraw pressurized air from the turboshaft engine and a duct for conveying the withdrawn air to the pneumatic circuit for supplying the pneumatic turbine with gas. The device further includes a sensor for determining the rotational speed of the pneumatic turbine.

First claim

The invention claimed is:

1. A device for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter, comprising a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with pressurised gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate said turboshaft engine and ensure that the turboshaft engine is reactivated, said testing device comprising:
an apparatus configured to withdraw pressurised air from the turboshaft engine;
a duct configured to convey said withdrawn pressurised air to said pneumatic circuit for supplying said pneumatic turbine; and
a sensor configured to determine the rotational speed of said pneumatic turbine.

2. The device according to claim 1 , further comprising an electrovalve arranged in a region of a joining point between the pneumatic circuit and said air-conveying duct, said electrovalve being configured to open an air passage between said air-conveying duct and said pneumatic circuit upon a command from a control unit and in the absence of a pressurised gas supply from said pneumatic circuit, and to close said air passage in the absence of a command or in the presence of a pressurised gas supply from said pneumatic circuit.

3. The device according to claim 2 , wherein said electrovalve comprises a preloaded spring configured to keep the air passage closed in the absence of a command or in the presence of a pressurised gas supply from said pneumatic circuit.

4. The device according to claim 1 , wherein said apparatus for withdrawing pressurised air from the turboshaft engine is arranged in a region of a compressor of said turboshaft engine.

5. A helicopter turboshaft engine provided with a rapid reactivation system, comprising a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with pressurised gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate said turboshaft engine and ensure that it is reactivated, further comprising a device for integrity testing said rapid reactivation system according to claim 1 .

6. A method for integrity testing a system for rapid reactivation of a turboshaft engine of a helicopter comprising a pneumatic turbine that is mechanically connected to said turboshaft engine and is supplied with pressurised gas, upon a command, by a pneumatic supply circuit such that it is possible to rotate said turboshaft engine and ensure that it is reactivated, the method comprising the steps of:
withdrawing pressurised air from the turboshaft engine;
conveying said air to said pneumatic turbine; and
measuring the rotational speed of said pneumatic turbine.

7. The method according to claim 6 , further comprising a step of comparing the measured rotational speed of said pneumatic turbine with a predetermined threshold speed.

8. The method according to claim 7 , wherein said air-conveying step comprises a step of commanding the opening of an electrovalve arranged in a region of a joining point between the pneumatic circuit and said air-conveying duct, said electrovalve being configured to open an air passage between said air-conveying duct and said pneumatic circuit upon a command from a control unit and in the absence of a pressurised gas supply from said pneumatic circuit, and to close said air passage in the absence of a command or in the presence of a pressurised gas supply from said pneumatic circuit.

9. The method according to claim 8 , further comprising a step of detecting if said electrovalve is opened in an untimely manner by means of a non-zero speed measurement for said pneumatic turbine in the absence of a command to open said electrovalve and when a procedure for rapid reactivation of the turboshaft engine is not in operation.

10. The method according to claim 6 , further comprising a step of saving speed measurements for said pneumatic turbine such that it is possible to monitor a trend for a state of the pneumatic turbine.

Assignees

• Safran Helicopter Engines

Inventors

• Thiriet Romain
• Bazet Jean-Michel
• Serghine Camel
• Marconi Patrick
• Irigoyen Jérôme
• Langford Stephen

Classifications

• F05D2260/83

  Testing, e.g. methods, components or tools therefor · CPC title

• F02C7/277 Primary

  the starter being a {separate} turbine · CPC title

• F05D2270/304

  Spool rotational speed · CPC title

• F02C6/08 Primary

  the gas being bled from the gas-turbine compressor · CPC title

• F05D2260/80

  Diagnostics · CPC title